Linear dynamics and distributed control of piezoelectric laminated continua have been intensively studied in recent years. In this paper, dynamics, electromechanical couplings, and control of piezoelectric laminated circular plates with an initial non-linear large deformation are investigated. It is
DYNAMICS AND DISTRIBUTED CONTROL OF CONICAL SHELLS LAMINATED WITH FULL AND DIAGONAL ACTUATORS
โ Scribed by H.S. TZOU; D.W. WANG; W.K. CHAI
- Publisher
- Elsevier Science
- Year
- 2002
- Tongue
- English
- Weight
- 501 KB
- Volume
- 256
- Category
- Article
- ISSN
- 0022-460X
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โฆ Synopsis
Nozzles, rocket fairings and many engineering structures/components are often made of conical shells. This paper focuses on the "nite element modelling, analysis, and control of conical shells laminated with distributed actuators. Electromechanical constitutive equations and governing equations of a generic piezo(electric)elastic continuum are de"ned "rst, followed by the strain}displacement relations and electric "eld}potential relations of laminated shell composites. Finite element formulation of a piezoelastic shell element with non-constant LameH parameters is brie#y reviewed; element and system matrix equations of the piezoelastic shell sensor/actuator/structure laminate are derived. The system equation reveals the coupling of mechanical and electric "elds, in which the electric force vector is often used in distributed control of shells. Finite element eigenvalue solutions of conical shells are compared with published numerical results "rst. Distributed control of the conical shell laminated with piezoelectric shell actuators is investigated and control e!ects of three actuator con"gurations are evaluated.
๐ SIMILAR VOLUMES
Vibration of a laminated composite plate is controlled by passive and active control methods. Stiffness change in composite structures by changes in laminate orientation is used as an example of a passive control method, negative velocity feedback control with the piezoelectric sensor/actuator is us
An integrated approach is given to determine the optimal levels of hybridization and feedback control force for symmetric, cross-ply laminates. The optimization objectives are the maximization of the biaxial buckling load and the minimization of the vibrational energy subject to constraints on the t